For modern aircrafts maneuvering control and reduction of power loss is a matter of great concern in Aerodynamics. Separation of airflow over the wings of aircraft at high angle of attack or at other situations is a hindrance to proper maneuvering control. As flow separation increases drag force on the aircraft, it consumes excess power. For these reasons much effort and research has gone into the design of aerodynamic surfaces which delay flow separation and keep the local flow attached for as long as possible. One of the simple and cost-effective way is to use a hinged flap on the wing of the aircraft, which lifts and self-adjusts to a position dependent on the aerodynamic forces and flap weight due to reversed flow at increasing angle of attack. There is a limitation of this kind of process. At very high angles of attack, the reversed flow would cause the flap to tip forwards entirely and the effect of the flap would vanish. For recovering this limitation an idea of controlling the movement or rotation of the flap has been proposed in this paper. A light surface was selected as a flap and was coupled to the shaft of a servo motor, which was placed on a model airfoil. For controlling the angle of rotation of the motor as well as the flap arbitrarily, an electronic circuit comprising necessary components was designed and applied to the servo motor successfully.

1.
J. P.
Johnston
,
M.
Nishi
, “
Vortex Generator Jets-Means for Flow Separation Control
,”
AIAA Journal
, vol.
28
, no.
6, June
1990
.
2.
K. M.
Manus
,
J.
Magill
, “
Separation Control in Incompressible and Compressible Flows Using Pulsed Jets,” in
Proceedings of the 27ᵗʰ AIAA Fluid Dynamics Conference
,
New Orleans, LA
,
June 17-20, 1996
.
3.
A.
Seifert
,
A.
Darabi
,
I.
Wygnanski
, “
Delay of Airfoil Stall by Periodic Excitation
,”
Journal of Aircraft
, vol.
33
, no.
4
,
July-August 1996
.
4.
A.
Seifert
,
S.
Eliahu
,
D.
Greenblatt
,
I.
Wygnanski
, “
Use of Piezoelectric Actuators for Airfoil Separation Control
,”
AIAA Journal
, vol.
36
, no.
8
, August
1998
.
5.
M. L.
Post
,
T. C.
Corke
, “
Separation Control on High Angle of Attack Airfoil Using Plasma Actuators
,”
AIAA Journal
, vol.
42
, no.
11
, November,
2004
.
6.
M.
Schatz
,
T.
Knacke
,
F.
Thiele
,
R.
Meyer
,
W.
Hage
and
D.W.
Bechert
, “
Separation Control by Self-Activated Movable Flaps,” in
Proceedings of the 42ⁿᵈ AIAA Aerospace Sciences Meeting & Exhibit
,
Reno, NV
,
2004
.
7.
W.
Liebe
, “
Der Auftrieb am Trag°Äugel: Entstehung und Zusammenbruch
,”
Aerokurier
, vol.
12
, pp.
1520
1523
,
1979
.
8.
B.
Malzbender
, “
Projekte der FV Aachen, Erfolge im Motor - und Segelflug
,”
Aerokurier
, vol.
1
, p.
4
,
1984
.
9.
G.
Patone
,
W.
Muller
, “Aeroflexible Oberflachenklappen als “RÄuckstrombremsen” nach dem Vorbild der Deckfedern des Vogelflugels,” TR-96-05,
Technische Universitat Berlin
,
1996
.
10.
D. W.
Bechert
,
M.
Bruse
,
R.
Meyer
,
W.
Hage
, “
Biological surfaces and their technological application - laboratory and flight experiments on drag reduction and separation control
,”
AIAA Paper 97-1960
,
Snowmass Village, CO
,
1997
.
This content is only available via PDF.
You do not currently have access to this content.